CN1311901A - Flexible, folable solar generator for spacecrafts - Google Patents
Flexible, folable solar generator for spacecrafts Download PDFInfo
- Publication number
- CN1311901A CN1311901A CN99809330.0A CN99809330A CN1311901A CN 1311901 A CN1311901 A CN 1311901A CN 99809330 A CN99809330 A CN 99809330A CN 1311901 A CN1311901 A CN 1311901A
- Authority
- CN
- China
- Prior art keywords
- array
- solar
- battery cell
- solar battery
- flap
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/428—Power distribution and management
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S136/00—Batteries: thermoelectric and photoelectric
- Y10S136/291—Applications
- Y10S136/292—Space - satellite
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- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention aims at providing a cost-effective, flexible, foldable solar generator for use in a spacecraft. According to the invention, this is achieved in that the current conductor path system consists of an inner current conductor path system (4) and an outer current conductor path system (5), the current conductor path systems (4, 5) are disposed outside the blanket (2) supporting the solar cells and the parallel circuits are shaped in the form of meanders while the series circuits (8) of the solar cells (7) are U-shaped. The invention can be used in a solar generator for spacecrafts, which consists of at least one foldable array with an integrated current conductor path system, wherein the array has several flexible blankets fitted with solar cells, the individual blankets are interconnected by hinges perpendicular to the direction of folding of the array and the solar cells are disposed in several electrical parallel and series circuits in the array.
Description
The present invention relates to flexible, Foldable solar energy battery as claimed in claim 1.
This solar cell is designed to big and light carrier structure, and preferably by what easily bend, the sheet substrate of concertina fold constitutes for it, and struts in orbit in large area by the mechanism of the mirror of looking in the distance.
The surface of these thin slices must be folding mutually to obtain the little space of carrying with the very little spacing of about 2mm only, the sheet plane carrier of each large-area moduleization of solar cell joint is equipped with an electric current circuit system, and it is applicable in mode simple and that be suitable for aerospace and links each joint.Electric current circuit system must satisfy the high request of aerospace fully, for example the high heat exchange duty and the highest reliability on the whole work duration that cause of the sun and earth's shadow.Electric in addition connection unit is design so, and no matter when make does not all have tensile stress.In order to change and keep in repair the whole solar cell joint, also should be able to repeatedly nondestructively take apart and binding again.
DE3210312C2 discloses a kind of solar cell that is used for spacecraft, and it saves synthetic obtaining by each sheet plane carrier.Each joint links mutually by means of the hinge of piano band mode.The output material that is used for the sheet plane carrier is the polyimide that single or double applies copper.
The back side of solar cell has the electrical current line system that is made of photograph-engraving method.Each current circuit that is used to transmit the electric current that solar cell obtains causes gang socket on the satellite through the whole length of solar cell distance far away like this internally from the sheet plane carrier joint of outside.The current circuit of next sheet plane carrier joint is close to the unilateral carrier joint of outer thin and begins from the centre to extend after being input to the centre, and and so on, thereby the whole back side obtains a pine tree formula, inwardly the circuit etching density that increases.All current circuit begins on the positive or negative joint of solar module.These link testers are crossed fold line and process hinge axis with folding-line channel and are guided to the joint terminal with joint-line channel.Such current circuit system is expensive in material and production, and obviously increases the weight of solar cell, thereby has increased the launch cost of spacecraft.
Task of the present invention is to provide a kind of cheapness, and variable is folding, is used for the solar cell of spacecraft.
Task of the present invention is finished by the described feature of claim 1.Other scheme of the present invention is as described in other claim.
The present invention has advantage ground to adopt a kind of design of special binding solar cell, and it makes does not have current circuit fully in array surface inside.
Special advantage is except the saving of production and Master Cost: owing to there is not current circuit in array surface, do not cause the through hole plating of job failure again easily, so in light weight.
Below by the description of drawings embodiments of the invention.In the accompanying drawing,
Fig. 1 is the sketch of an array,
Fig. 2 is the solar cell ordering catenation principle figure of array,
Fig. 3 is the array flap (blanket) with internal current line system,
Fig. 4 is an array flap with foreign current line system,
Fig. 5 is a solar cell-little module of array, and
Fig. 6 is hinge between adjacent flap-be connected with lead design.
Array 1 shown in Figure 1 as an example is by 33 blocks of flaps 2 (for 4 that only show among viewability Fig. 1 wherein) that are loaded with solar cell, an internal current line system 4, a foreign current line system 5, hinge 6, be welded as the solar battery cell 7 of little module 3,14, the substrates 11 of terminal contact and the block pressur plate 12 that are welded between little module are formed.
In the embodiment shown, flap 2 is made of a polyimide with glass fibre lamination, and has the size of 3352mm * 285mm.Each flap 2 is equipped with solar battery cell 7 on its surface, and per 10 synthesize a little module 3 in them.On each flap 2,18 little module 3 direct neighbor ground are so arranged, and the direction that the solar battery cell ordering connects is parallel to the shorter size limit of flap 2.In other connectivity scenario of solar battery cell, other arrangement on the flap is necessary.Two longer sides of flap along on, one side of something of the hinge 6 of a piano shape of extending by whole flap edge is installed, and half of hinge designed so, it is corresponding with the half of hinge of adjacent flap.
The distance that each little module of flap 2 is 3 is 1mm except two exceptions.Exception is the wide spacing of 1.5mm 15, and it is used to reduce the spark-over field intensity between the little module with high potential difference.
The current circuit system is formed on the easily curved flap equally, and its size is corresponding to the flap 2 that is loaded with solar battery cell.With spacecraft directly in abutting connection with, the inner internal current line system of installing 4 on a long limit with substrate 11 mechanical link, on relative long limit by the flap mechanical link that be loaded with solar battery cell of hinge 6 with inside.Electric wiring between the little module 3 of the flap of current circuit system 4 and inside connects to be finished by means of the terminal contact that welds together of current circuit system and little module in common mode.Be arranged in array 1 from spacecraft farthest, foreign current line system 5 on the external position is accordingly with the flap machinery that is loaded with solar battery cell of outside be electrically connected.The outer minister limit of current circuit system 5 and pressing plate 12 mechanical link.
Schematic diagram shown in Fig. 2 is that the electric parallel ordering of solar battery cell on the array 1 connects 8 the structure and the embodiment of arrangement.Ordering connects a branch road a who comprises the solar battery cell that links one by one on 8 principles
1(b
1..., h
1, i
1) (branch road only is expressed as a line simply in Fig. 2), second of the solar battery cell of Lian Jieing branch road a one by one
2(b
2..., h
2, i
2), it is compared with first branch road has opposite solar cell polarity arrangement, the electric lead 10 in the current circuit system 5 externally, it couples together two branch roads on electric one by one, and two leads 9 on the internal current line system 4, they connect ordering and connect 8 energy supply systems to spacecraft.
Branch road with the solar battery cell that links one by one extends on the direction that array 1 launches along the whole flap 2 that is loaded with solar battery cell point-blank.Ordering connects the polar orientation of solar battery cell in 8 each branch roads and represents with the arrow on the branch road in Fig. 2, the direction that current potential increases in its expression branch road.The face of the installation solar battery cell of array 1 does not illustrate each flap 2 simply in Fig. 2, and represents with label F.The ordering that obtains as mentioned above being made of two branch roads that couple together one by one with electric lead 10 connects 8, and it has U-shaped.
Arranged 9 orderings in an embodiment on the array 1 and connected 8, but 4 orderings that for clarity sake only show in Fig. 2 wherein connect 8.The ordering of embodiment connects 8 branch road a
1..., i
2Form by two electric parallel connected sequences, thereby an ordering connection 8 comprises 660 solar cells 7 with 165 solar battery cells 7 that link one by one.Other connected mode of solar battery cell is possible, and it depends on the power requirement to solar cell.
Fig. 3 illustrates the internal current line system 4 of the electric lead 9 that has on the flap.
The branch road of ordering connection 8 is arranged on the array 1 with a definite arrangement in the embodiment of this explanation.This ordering is so to select: the maximum potential difference between the solar battery cell that occurs adjacent legs on two positions of array 1 only.Fig. 3 label a
1..., i
2Be shown to the interface arrangement of the electric lead 9 of not shown branch road.Branch road is arranged on the array 1 in the following order: a
1-b
1-c
1-d
1-e
2-f
2-g
2-h
2-i
2-a
2-b
2-c
2-d
2-e
1-f
1-g
1-h
1-i
1With this order, only at branch road to d
1And e
2And branch road is to d
2And e
1Between install on " inside " edge of face F of solar battery cell and maximum potential difference occurs.Right little module 3 space on flap 2 of these branch roads is a spacing 15, and it has 1.5mm wide.
Another feature of ordering is branch road a
2..., i
2Mutually by arrangement, thereby because current potential is equal, the electric lead 9 of these 9 branch roads is synthesized to two and collects the energy supply system of presenting on the line 16 to spacecraft.Yet this is not mandatory essential.
Fig. 4 illustrates foreign current line system 5, and its structure is same as internal current line system 4 except the structure of electric lead.In the electric lead 10 each connects branch road a
1..., i
2Two, they constitute U-shaped ordering together and connect 8.Following for this reason branch road is to being synthesized: a
1And a
2, b
1And b
2..., h
1And h
2, i
1And i
2Branch road a to array 1
1..., i
2Being arranged among Fig. 4 of electric lead 10 illustrate with label, and branch road is not shown.
Fig. 5 illustrates the structure of little module 3.In an embodiment, per 10 solar battery cells 7 are welded as a little module and paste the public cover glass of lastblock by solar battery cell connector 13.Solar battery cell 7 per 5 solar battery cells that link one by one in little module 3 are arranged in two adjacent row.The terminal connecting terminal contact 14 of two row.Terminal contact 14 is designed so that to exist the parallel connection of two row in little module 3.Terminal contact also can be connected under other the electric design conditions of solar cell.
Utilize terminal contact 14, the adjacent little module 3 of adjacent flap 2 couples together as shown in Figure 6 one by one with the method for being familiar with.The length of little module 3 is consistent with the bond length of flap 2, thereby terminal contact 14 is realized with the scope that is connected hinge 6 of the fold line of array 1 is interior.Terminal contact 14 makes the bending that scrolls up that appears at visible terminal contact 14 welded together among Fig. 6 in welding during two terminal contacts 14 on fold line.This crooked advantage is not have the effect of mechanical load when folded array on terminal contact 14.
Claims (5)
1. the solar cell that is used for spacecraft, it is folding by at least one, array with the current circuit system in array is formed, and array has a plurality of easily curved flaps that are loaded with solar battery cell, each flap interconnects with hinge on the direction of the direction of launching perpendicular to array, and solar battery cell is being arranged in a plurality of being connected in parallel and being connected in series on electric on the array, it is characterized in that, the current circuit system is made of an internal current line system (4) and a foreign current line system (5), current circuit system (4,5) be arranged at outside the flap (2) that is loaded with solar battery cell, being connected in parallel of solar battery cell (7) is designed to having many bends or curves shape (meander shaped), and its be connected in series (8) are designed to U-shape, what two were extended on whole array (1) expansion direction in this connects, electric branch road (a that interconnective solar battery cell (7)
1I2) end points the outside of array, couple together one by one through the electric lead (10) of foreign current line system (5) on away from an edge of spacecraft, and the terminal of be connected in series (8) is connected to the energy supply system of spacecraft along last electric lead by internal current line system (4) (9) in the internal edges of array (1).
2. solar cell as claimed in claim 1 is characterized in that, inside and outside current circuit system (4,5) constitutes by integrated electric flat conductor on easily curved flap.
3. solar cell as claimed in claim 1 or 2 is characterized in that, the branch road (a of be used to be connected in series (8)
1..., i
2) so selected, only make on array 1 at two adjacent branch roads to (d
1And e
2And d
2And e
1) between maximum potential difference appears.
4. solar cell as claimed in claim 1 is characterized in that, the flap (2) that solar battery cell (7) are installed does not have the current circuit system that is made of integrated electric flat conductor.
5. solar cell as claimed in claim 1 is characterized in that, a plurality of arrays link like that according to claim 1 and are combined into a solar panel.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19836272A DE19836272C2 (en) | 1998-08-11 | 1998-08-11 | Flexible, foldable solar generator for spacecraft |
| DE19836272.2 | 1998-08-11 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1311901A true CN1311901A (en) | 2001-09-05 |
Family
ID=7877134
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN99809330.0A Pending CN1311901A (en) | 1998-08-11 | 1999-07-24 | Flexible, folable solar generator for spacecrafts |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US6543725B1 (en) |
| EP (1) | EP1110246A1 (en) |
| JP (1) | JP2002522926A (en) |
| CN (1) | CN1311901A (en) |
| DE (1) | DE19836272C2 (en) |
| WO (1) | WO2000010207A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108231927A (en) * | 2016-12-12 | 2018-06-29 | 株式会社丰田自动织机 | Solar cell module and electric conductor |
Families Citing this family (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2822436B1 (en) * | 2001-03-21 | 2003-08-15 | Cit Alcatel | SOLAR PANEL HAVING ELECTRICAL TERMINALS DISTRIBUTED ON ITS SURFACE |
| US6784359B2 (en) * | 2002-03-04 | 2004-08-31 | Microsat Systems, Inc. | Apparatus and method for the design and manufacture of foldable integrated device array stiffeners |
| FR2846298A1 (en) * | 2002-10-29 | 2004-04-30 | Cit Alcatel | ARTICULATED ASSEMBLY OF SOLAR GENERATOR PANELS AND SPATIAL VEHICLE |
| US7888584B2 (en) * | 2003-08-29 | 2011-02-15 | Lyden Robert M | Solar cell, module, array, network, and power grid |
| JP4518973B2 (en) * | 2005-02-16 | 2010-08-04 | シャープ株式会社 | Solar cell and method for manufacturing the same |
| US8683755B1 (en) * | 2010-01-21 | 2014-04-01 | Deployable Space Systems, Inc. | Directionally controlled elastically deployable roll-out solar array |
| FR2969985B1 (en) | 2010-12-30 | 2016-09-09 | Thales Sa | SOLAR PLANAR GENERATOR |
| CN102320383B (en) * | 2011-06-23 | 2014-01-22 | 哈尔滨工业大学 | Double-omega-shaped carbon fiber composite material expansion arm and stretching method thereof |
| US9102422B2 (en) * | 2012-06-28 | 2015-08-11 | Solaero Technologies Corp. | Solar cell assembly, solar cell panel, and method for manufacturing the same |
| US10090430B2 (en) | 2014-05-27 | 2018-10-02 | Sunpower Corporation | System for manufacturing a shingled solar cell module |
| US11942561B2 (en) | 2014-05-27 | 2024-03-26 | Maxeon Solar Pte. Ltd. | Shingled solar cell module |
| US11482639B2 (en) | 2014-05-27 | 2022-10-25 | Sunpower Corporation | Shingled solar cell module |
| US20150349176A1 (en) * | 2014-05-27 | 2015-12-03 | Cogenra Solar, Inc. | High voltage solar panel |
| US10861999B2 (en) | 2015-04-21 | 2020-12-08 | Sunpower Corporation | Shingled solar cell module comprising hidden tap interconnects |
| US10189583B2 (en) * | 2015-05-13 | 2019-01-29 | Analytical Mechanics Associates, Inc. | Deployable sheet material systems and methods |
| WO2017120432A1 (en) | 2016-01-06 | 2017-07-13 | Roccor, Llc | Extendible membrane systems, devices, and methods |
| US11569395B2 (en) | 2016-04-22 | 2023-01-31 | Mitsubishi Electric Corporation | Solar power generator, solar array wing, and space structure |
| US11967923B2 (en) * | 2018-03-28 | 2024-04-23 | The Boeing Company | Single sheet foldout solar array |
| DE102018117993B4 (en) * | 2018-07-25 | 2020-06-18 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Spacecraft membrane unit and spacecraft membrane package with a spacecraft membrane unit |
| US10840707B2 (en) | 2018-08-06 | 2020-11-17 | Robert M. Lyden | Utility pole with solar modules and wireless device and method of retrofitting existing utility pole |
| US11207988B2 (en) | 2018-08-06 | 2021-12-28 | Robert M. Lyden | Electric or hybrid vehicle with wireless device and method of supplying electromagnetic energy to vehicle |
| US11588421B1 (en) | 2019-08-15 | 2023-02-21 | Robert M. Lyden | Receiver device of energy from the earth and its atmosphere |
| CN112636695A (en) * | 2020-12-15 | 2021-04-09 | 华能新能源股份有限公司 | System and method for repairing output power of series solar cell |
| CN112865689B (en) * | 2021-01-04 | 2022-03-25 | 上海宇航系统工程研究所 | Split type diaxon actuating mechanism |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3210312A1 (en) | 1982-03-20 | 1983-09-22 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Electrical current conductor track system for space vehicle solar generators |
| JPS60147152A (en) | 1984-01-10 | 1985-08-03 | Nec Corp | Solar battery panel |
| US4652693A (en) * | 1985-08-30 | 1987-03-24 | The Standard Oil Company | Reformed front contact current collector grid and cell interconnect for a photovoltaic cell module |
| JP3077906B2 (en) | 1989-03-09 | 2000-08-21 | 株式会社東芝 | Deployable solar cell paddle |
| JPH03262800A (en) | 1990-03-12 | 1991-11-22 | Mitsubishi Electric Corp | Solar cell paddle |
| US5298085A (en) * | 1992-03-24 | 1994-03-29 | Aec-Able Engineering Company, Inc. | Support blanket for solar cell arrays |
| US5961738A (en) * | 1997-07-30 | 1999-10-05 | Aec-Able Engineering Co., Inc. | Solar array for satellite vehicles |
| US6291761B1 (en) * | 1998-12-28 | 2001-09-18 | Canon Kabushiki Kaisha | Solar cell module, production method and installation method therefor and photovoltaic power generation system |
| US6624351B2 (en) * | 2001-11-08 | 2003-09-23 | Ecosol Solar Technologies Ltd. (Usa) | Folding photovoltaic strip device |
-
1998
- 1998-08-11 DE DE19836272A patent/DE19836272C2/en not_active Expired - Fee Related
-
1999
- 1999-07-24 WO PCT/DE1999/002278 patent/WO2000010207A1/en not_active Application Discontinuation
- 1999-07-24 US US09/762,666 patent/US6543725B1/en not_active Expired - Fee Related
- 1999-07-24 CN CN99809330.0A patent/CN1311901A/en active Pending
- 1999-07-24 EP EP99948681A patent/EP1110246A1/en not_active Withdrawn
- 1999-07-24 JP JP2000565571A patent/JP2002522926A/en not_active Withdrawn
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108231927A (en) * | 2016-12-12 | 2018-06-29 | 株式会社丰田自动织机 | Solar cell module and electric conductor |
Also Published As
| Publication number | Publication date |
|---|---|
| US6543725B1 (en) | 2003-04-08 |
| EP1110246A1 (en) | 2001-06-27 |
| JP2002522926A (en) | 2002-07-23 |
| WO2000010207A1 (en) | 2000-02-24 |
| DE19836272A1 (en) | 2000-02-17 |
| DE19836272C2 (en) | 2003-08-07 |
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Legal Events
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|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |